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公开(公告)号：US20140252160A1
公开(公告)日：2014-09-11
申请号：US14190150
申请日：2014-02-26
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry
IPC: B64D27/12
CPC classification number: B64D27/12 , F02C3/10 , F02C3/107 , F02K3/077 , F05D2210/40 , F05D2230/50 , F05D2230/72 , F05D2250/30 , F05D2250/314 , Y10T29/49721
Abstract: An engine mounting arrangement includes a propulsor mounted to an aircraft wing, and an engine core aerodynamically connected to the propulsor and positioned rearward of the propulsor.
Abstract translation: 发动机安装装置包括安装在飞行器机翼上的推进器以及空气动力学连接到推进器并位于推进器后方的发动机核心。
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公开(公告)号：US20140205439A1
公开(公告)日：2014-07-24
申请号：US14219112
申请日：2014-03-19
Applicant: United Technologies Corporation
Inventor： Brian D. Merry , Gabriel L. Suciu , Karl L. Hasel
CPC classification number: F02C7/06 , F01D25/162 , F02C3/04 , F02C3/107 , F02C7/36 , F02K3/00 , F02K3/04 , Y02T50/671 , Y10T29/4932
Abstract: A gas turbine engine includes a housing including an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A geared architecture is arranged within the inlet case. The geared architecture includes an epicyclic gear train. A fan is rotationally driven by the geared architecture. A shaft provides a rotational axis. A hub is operatively supported by the shaft. First and second bearings support the shaft relative to the intermediate case and the inlet case, respectively.
Abstract translation: 燃气涡轮发动机包括壳体，其包括分别设置入口壳体流动路径和中间壳体流动路径的入口壳体和中间壳体。 入口箱内设有齿轮架构。 齿轮架构包括行星齿轮系。 风扇由齿轮架构旋转驱动。 轴提供旋转轴。 轮毂由轴可操作地支撑。 第一和第二轴承分别相对于中间壳体和进气口支撑轴。
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193.发明申请Gas Turbine Engine Having Fan Rotor Driven by Turbine Exhaust and With a Bypass 有权燃气轮机发动机，风机转子由涡轮排气和旁路驱动公开(公告)号：US20140183296A1
公开(公告)日：2014-07-03
申请号：US13731371
申请日：2012-12-31
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Jesse M. Chandler
Abstract: A gas turbine engine has a core engine incorporating a core engine turbine. A fan rotor is driven by a fan rotor turbine. The fan rotor turbine is in the path of gases downstream from the core engine turbine. A bypass door is moveable from a closed position at which the gases from the core engine turbine pass over the fan rotor turbine, and moveable to a bypass position at which the gases are directed away from the fan rotor turbine. An aircraft is also disclosed.
Abstract translation: 燃气涡轮发动机具有并入有核心发动机涡轮机的核心发动机。 风扇转子由风扇转子涡轮机驱动。 风扇转子涡轮机处于来自核心发动机涡轮机下游的气体的路径。 旁路门可以从关闭位置移动，在该关闭位置，来自核心发动机涡轮机的气体通过风扇转子涡轮机，并且可移动到旁路位置，在该旁路位置，气体被引导离开风扇转子涡轮机。 还披露了一架飞机。
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公开(公告)号：US20140157756A1
公开(公告)日：2014-06-12
申请号：US14179771
申请日：2014-02-13
Applicant: United Technologies Corporation
Inventor： Karl L. Hasel , Joseph B. Staubach , Brian D. Merry , Gabriel L. Suciu , Christopher M. Dye
IPC: F02K3/06
CPC classification number: F02K3/06 , F02C3/107 , F05D2260/4031
Abstract: A gas turbine engine has a fan section, including a fan, a gear arrangement configured to drive the fan section, the geared arrangement defining a gear reduction ratio greater than or equal to about 2.6. A compressor section includes both a first compressor and a second compressor. A turbine section is configured to drive the compressor section and the gear arrangement. An overall pressure ratio is provided by the combination of the first compressor and the second compressor.
Abstract translation: 燃气涡轮发动机具有风扇部分，其包括风扇，构造成驱动风扇部分的齿轮装置，齿轮装置限定大于或等于约2.6的齿轮减速比。 压缩机部分包括第一压缩机和第二压缩机。 涡轮部分构造成驱动压缩机部分和齿轮装置。 总压力比由第一压缩机和第二压缩机的组合提供。
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公开(公告)号：US20140157754A1
公开(公告)日：2014-06-12
申请号：US14179640
申请日：2014-02-13
Applicant: United Technologies Corporation
Inventor： Karl L. Hasel , Joseph B. Staubach , Brian D. Merry , Gabriel L. Suciu , Christopher M. Dye
IPC: F02K3/06
CPC classification number: F02C7/36 , F01D5/06 , F01D5/12 , F01D9/02 , F01D21/003 , F01D25/24 , F01D25/28 , F02C3/04 , F02C3/06 , F02C3/107 , F02C7/06 , F02C7/28 , F02C9/18 , F02K3/025 , F02K3/06 , F05D2220/32 , F05D2220/323 , F05D2240/12 , F05D2240/35 , F05D2240/55 , F05D2260/40 , F05D2260/4031 , F05D2260/40311
Abstract: A gas turbine engine has a fan section, including a fan, a gear arrangement configured to drive the fan section, and a compressor section, including both a first compressor and a second compressor. A turbine section is configured to drive the compressor section and the gear arrangement. An overall pressure ratio is provided by the combination of the first compressor and the second compressor, with the overall pressure ratio being greater than or equal to about 35. A pressure ratio across the fan section is less than or equal to about 1.50. The fan is configured to deliver a portion of air into the compressor section, and a portion of air into a bypass duct.
Abstract translation: 一种燃气涡轮发动机具有风扇部分，包括风扇，构造成驱动风扇部分的齿轮装置和包括第一压缩机和第二压缩机的压缩机部分。 涡轮部分构造成驱动压缩机部分和齿轮装置。 总压力比由第一压缩机和第二压缩机的组合提供，总压力比大于或等于约35.风扇部分的压力比小于或等于约1.50。 风扇被配置为将一部分空气输送到压缩机部分中，并且一部分空气进入旁通管道。
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Patent Agency Ranking
公开(公告)号：US20140157753A1
公开(公告)日：2014-06-12
申请号：US14179864
申请日：2014-02-13
Applicant: United Technologies Corporation
Inventor： Karl L. Hasel , Joseph B. Staubach , Brian D. Merry , Gabriel L. Suciu , Christopher M. Dye
IPC: F02K3/06
CPC classification number: F02K3/06 , F02C3/107 , F05D2260/4031
Abstract: A method of designing a gas turbine engine includes providing a fan section including a fan; driving the fan section via a gear arrangement; providing a compressor section, including both a first compressor and a second compressor; and driving the compressor section and the gear arrangement via a turbine section. An overall pressure ratio, being provided by the combination of a pressure ratio across the first compressor and a pressure ratio across the second compressor, is greater than or equal to about 35. The pressure ratio across the first compressor is greater than or equal to about 7.
Abstract translation: 一种设计燃气涡轮发动机的方法包括：提供包括风扇的风扇部分; 通过齿轮装置驱动风扇部分; 提供包括第一压缩机和第二压缩机的压缩机部分; 并且经由涡轮机部分驱动压缩机部分和齿轮装置。 通过跨第一压缩机的压力比和跨第二压缩机的压力比的组合提供的总压力比大于或等于约35.跨第一压缩机的压力比大于或等于约 7。
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197.发明申请公开(公告)号：US20140117152A1
公开(公告)日：2014-05-01
申请号：US13662879
申请日：2012-10-29
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Jesse M. Chandler , Joseph B. Staubach , Adam Joseph Suydam
Abstract: A gas turbine engine has a core engine incorporating a turbine, and a manifold positioned downstream of the turbine. The manifold delivers gas downstream of the turbine into at least two nacelles, with each of the nacelles receiving a fan rotor. The fan rotor is fixed to rotate with a tip turbine mounted at a radially outer location of the fan rotor, with the tip turbine being in the path of gases from the manifold. An aircraft is also disclosed.
Abstract translation: 燃气涡轮发动机具有并入涡轮机的核心发动机和位于涡轮机下游的歧管。 歧管将涡轮下游的气体输送到至少两个机舱中，其中每个机舱都接收风扇转子。 风扇转子被固定以与安装在风扇转子的径向外部位置处的尖端涡轮一起旋转，其中尖端涡轮机处于来自歧管的气体的路径中。 还披露了一架飞机。
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公开(公告)号：US11608784B2
公开(公告)日：2023-03-21
申请号：US16274340
申请日：2019-02-13
Applicant: United Technologies Corporation
Inventor： Hung Duong , Marc J. Muldoon , Gabriel L. Suciu
Abstract: A gas turbine engine has a low speed input shaft drives a first plurality of accessories. A high speed input shaft drives a second plurality of accessories. The first plurality of accessories rotating about a first set of rotational axes perpendicular to a first plane. The second plurality of accessories rotating about a second set rotational axes perpendicular to a second plane. The first and second planes extending in opposed directions away from a drive input axis. Compressed air is tapped and passes through a heat exchanger, then to a boost compressor, and then to at least one rotatable components in a main compressor section and a main turbine section. The boost compressor driven on a boost axis, which is non-parallel to the first set of rotational axes and the second set of rotational axes.
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公开(公告)号：US11118481B2
公开(公告)日：2021-09-14
申请号：US15424930
申请日：2017-02-06
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian Merry , Ioannis Alvanos
Abstract: A turbine exhaust assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a turbine exhaust case comprised of CMC material and attachable to a turbine case, a tail cone comprised of CMC material that has a leading edge and a trailing edge, and an exhaust mixer comprised of CMC material and coupled to the turbine exhaust case. The exhaust mixer has a plurality of lobes arranged about the tail cone to define an exhaust flow path. A plurality of struts extend from the tail cone to support the exhaust mixer at a location aft of the leading edge of the tail cone. A method of assembling a propulsion system is also disclosed.
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公开(公告)号：US11073087B2
公开(公告)日：2021-07-27
申请号：US14187612
申请日：2014-02-24
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry
Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan rotatable about an engine axis with a plurality of fan blades rotatable about a fan blade axis. A geared architecture is in communication with the fan and driven by a turbine section. The fan rotates at a first speed and the turbine section rotates at a second speed different from the first speed and a fixed area fan nozzle in communication with the fan section.
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